Preconditioned air connector assembly for aircraft

ABSTRACT

A connector for coupling a preconditioned air source to an aircraft is provided. The connector comprises actuating members rotatably secured to a body. In one embodiment, the actuating members are supported, at least partially, by an integrated bearing assembly. The connector also comprises securing members that are positionably coupled to the actuating members. Accordingly, rotation of the actuating members displaces the securing members. Moreover, the actuating members comprise respective camming surfaces, wherein the camming surfaces define the axial position of the corresponding securing members.

FIELD OF THE INVENTION

[0001] The present technique relates to a connector assembly foraircraft. More particularly, the technique relates to a connectorassembly, couplable to an aircraft, for routing preconditioned air tothe aircraft while parked.

BACKGROUND OF THE INVENTION

[0002] While an aircraft is in flight, various subsystems within theaircraft maintain a comfortable cabin environment. For example, thesesubsystems may provide electricity, maintain cabin pressure or controlthe circulation and temperature air within the cabin. When on theground, however, in an effort to conserve power and the life expectancyof aircraft components, these subsystems may be at least partiallydeactivated. Upon deactivation of the climate control subsystem, forexample, the conditions within the aircraft may become undesirable forthe maintenance crew preparing the aircraft for the next flight or forpassengers boarding or deplaning. Accordingly, many airports providedocking stations which, when coupled to the aircraft, substitute for theaircraft's subsystems.

[0003] In one such example, it is common practice in the airtransportation industry to provide preconditioned air (PCA) to anaircraft docked at a gate. Typically, the preconditioned air is routedfrom a ground source, through a flexible conduit and into the aircraft.In completing the routing, a PCA connector is provided to securelycouple the conduit to the aircraft. Because PCA connectors are coupledto various types of aircraft, aircraft manufactures as well as PCAconnector manufacturers have traditionally adhered to a common design.More particularly, the design specifications as set forth in MilitaryStandards MS33562 (ASG) entitled “Connection, Aircraft Ground AirConditioning, 8 inch, minimum requirements.”

[0004] This uniformity in design permits the same PCA connector to beused at airports worldwide. Accordingly, PCA connectors are subject toenvironmental conditions that range from tropical to artic tundra toarid dessert. Moreover, the frequency with which PCA connectors areengaged and disengaged from a given aircraft suggests the desirabilityof a durable and sturdy design. All too often, PCA connectors have beenknown to be disengaged from the aircraft and subsequently dropped,approximately 8-10 feet, to the ground. This can dent, deform orotherwise damage conventional connectors. Accordingly, the need existsfor a novel PCA connector which addresses many of the foregoingconcerns.

SUMMARY OF THE INVENTION

[0005] The present technique may be used for a wide-variety ofapplications, however, the technique is particularly well suited for PCAconnectors. In one embodiment of the present technique, the PCAconnector comprises a body having an integrated bearing structure. Thebearing structure at least partially supports a pivoting member coupledto the connector. Additionally, a displaceable member is coupled to thepivoting member such that pivotal actuation of the pivoting memberdirects the displaceable member from a first position to a secondposition.

[0006] The present technique also provides a PCA connector comprising acamming surface disposed within a slot of an actuation member which isrotatably coupled to a body. The camming surface engages with anengagement pin coupled to a displaceable member, wherein the interactionbetween the engagement pin and the camming surface biases thedisplaceable member from a first position to a second position.

[0007] In accordance with another aspect of the present technique, asystem for providing preconditioned air is provided. The systemcomprises a preconditioned air source coupled to the PCA connector via aconduit. The PCA connector comprises a rotating member coupled to adisplaceable member such that actuation of the rotating memberresultantly actuates the displaceable member. Moreover, displacement ofthe displaceable member may be limited to the axial direction withrespect to the connector.

[0008] The present technique also offers a method of securing a PCAconnector. The method comprises coupling a first member to a secondmember. The method further comprises driving the second member in anaxial direction with respect to the connector by pivoting the firstmember. Resultantly, the axial movement of the second member couples thePCA connector to an aircraft.

BRIEF DESCRIPTION OF THE DRAWINGS

[0009] The foregoing and other advantages and features of the inventionwill become apparent upon reading the following detailed description andupon reference to the drawings in which:

[0010]FIG. 1 is a top perspective view of an exemplary PCA connector,wherein the PCA connector is coupled to a flexible conduit representedin the figure in dashed lines;

[0011]FIG. 2 is an exploded view of the exemplary PCA connector of FIG.1 illustrating a number of exemplary features integrated into the bodyof the connector;

[0012]FIGS. 3A and 3B respectively illustrate plan and side views of anexemplary actuation member, wherein the actuation member includes acamming surface disposed within a slot; additionally, FIG. 3Aillustrates a locking portion located within the slot;

[0013]FIG. 4 is a cross-sectional view of the exemplary PCA connector ofFIG. 1 along line 4-4;

[0014]FIG. 5 illustrates a side view of the exemplary PCA connector inthe unlocked or open position; and

[0015]FIG. 6 illustrates a side view of the exemplary PCA connector astransitioning to the locked or closed position.

DETAILED DESCRIPTION OF SPECIFIC EMBODIMENTS

[0016] Referring generally to FIG. 1, an exemplary embodiment of a PCAconnector assembly 10 is illustrated. The exemplary PCA connectorassembly 10 comprises a PCA connector 12 having a flexible conduit 14coupled to one end and being coupled, at the opposite end, to anaircraft inlet 16. To provide preconditioned air to the aircraft, theflexible conduit 14 is coupled, at the distal end, to a preconditionedair source (not shown), typically provided by the airport facility ateach gate. Upon arrival of the aircraft at the gate, an operator maymanually align the connector 12 with the inlet 16 and, subsequently,secure the connector to the aircraft. Once fully secured, the PCAconnector assembly 10 provides a fluid flow path for the preconditionedair to travel from the source to the aircraft.

[0017] To facilitate this coupling, the PCA connector 12 comprises anumber of features. In one embodiment, the PCA connector 12 comprises atubular body 18 having integrated bearing structures 20. Only theexternal casings of the integrated bearing structures 20 are visible inthis figure. However, the internal features of the respective bearingstructures 20 are further described in greater detail below.

[0018] As discussed above, the connector 12 may be subject to harshenvironments and operator abuse. Keeping this in mind, the connector 12,for optimal use, may be designed to withstand changes in climate thatcan induce thermal cracking, unwanted expansion and corrosion intraditional connectors. Accordingly, the connector 12 may compriseZytel®, an injection moldable nylon resin available from the DuPontCompany. This material provides excellent strength characteristics overa large range of temperature and moisture conditions. Moreover, thismaterial is extremely resistant to corrosion. Accordingly, Zytel®presents characteristics desirable to the construction of the instantconnector 12. However, other materials are also envisaged. For example,many other types of injection-moldable plastics such as HDPE may providesuitable performance, particularly as compared to traditional materials.Advantageously, injection molded plastics also provide a lightweightconstruction that permits an operator to easily manipulate and positionthe connector 12.

[0019] Returning to the components of the connector 12, a pair ofactuating members 22 are coupled to the body 18. Advantageously, theactuating members 22 may be employed to position the assembly 10 and mayalso be employed to provide actuation leverage, as further discussedbelow. To provide a more ergonomic gripping surface for the operator,cushioned grips 24 may be sheathed over the actuating members 22.Additionally, in the exemplary connector 12, covers 26, secured by aplurality of screws 28 threadingly engaged to the body 18, are disposedover a portion of the actuating members 22 and coupled to the bearingassembly 20.

[0020] The connector 12 further comprises a flange portion 30 thatextends along the perimeter of one side of the body 18. Structuralsupport may be provided to the flange 30 portion by integratedbuttresses 32 located optimally about the body 18. Features of theexemplary flange 30 are apertures 34 through which securing members 36partially extend. In this figure, only a clamping portion 38 of therespective securing members 36 is visible. However, other features ofthe securing members 36 are discussed more fully below. Also, as furtherdiscussed below, actuation of the securing members 36 facilitiescoupling of the exemplary connector 12 to the aircraft inlet 16.

[0021] Upon coupling of the connector 12 to the aircraft inlet 16,preconditioned air may be routed, under pressure, from thepreconditioned air source into the interior region of the flexibleconduit 14. From the conduit 14, the preconditioned air is then routedinto the aircraft inlet 16 through an interior region 40 of theconnector 12. To ensure that the conduit 14 remains coupled to connector12 during operation, a band clamp (not shown) may be disposed just abovestop ribs 42 and tightened. Accordingly, the band clamp imparts aradially inward force constraining the conduit on the connector 12 and,resultantly, aids in securing the conduit 14 to the connector 12.Additionally, a flexible seal 44 may be disposed between the flange 30and the inlet 16 to prevent the unwanted escape of preconditioned air.Once the preconditioned air route is assembled, preconditioned air maybe routed therethrough and subsequently distributed into the cabin andcockpit of the aircraft via an internal duct system (not shown).

[0022] Referring next to FIG. 2, a number of exemplary features that maybe integrated into the body 18 of the connector 12 are illustrated. Forexample, the body 18 may comprise an integrated guide channel 46. Whenassembled, at least a portion of the securing member 36 resides withinthe guide channel 46. Advantageously, to prevent the unwanted rotationaland radial movements of the securing member 36, the dimensions of theguide channel 46 are such that the guide channel 46 closely sheaths thesecuring member 36. In other words, the guide channel 46 may beconfigured to restrict movement of the securing member 36 to the axialor, based on the orientation of the present figure, up and downdirections. In the present embodiment, the guide channel 42 terminatesat the aperture 34, and, as such, only the clamping portion 38 of thesecuring member 36 remains accessible when the connector 12 isassembled.

[0023] Another feature integrated into the body 18 of the exemplaryconnector 12 may be an integrated bearing structure 48. In the exemplaryembodiment shown, the integrated bearing structure 48 provides supportto actuation member 22 which, in turn, is pivotably coupled to the body18, as well as to the securing member 36. Simply put, the bearingstructure 48 supports the radial and thrust loads imparted on theactuation member 22. By integrating the bearing assembly 48 into thebody 18, the likelihood of separation between the body 18 and thebearing support 48 is reduced. To the operator, the increased durabilitymay quickly translate into a reduction in maintenance expenses as wellas a reduction in down time.

[0024] Focusing on the pivotable coupling between the actuation member22 and the body 18, this coupling comprises a pivot pin 50 received byan integrated sleeve portion 52 of the bearing 48, wherein the sleeveportion 52 traverses into the interior region 40 of the connector 12. Inassembling the coupling, the pivot pin 50 may be coaxially insertedthrough a pivot opening 54 disposed on the actuation member 22 and,subsequently, through the integrated sleeve 52. After insertion of thepivot pin 50, the coupling may be secured by fastening a securing nut 56which may be threaded onto the portion of the pivot pin 50 extendingbeyond the sleeve 52 and into the interior region 40 of the connector12. If so desired, washers 58 may be coaxially placed between the pin 50and the actuation member 22 as well as between securing nut 56 and thebody 18. As assembled, the coupling allows rotation of the actuationmember 22, while the bearing structure 48 supports the radial and thrustloads and prevents undesired movement of the actuation member 22 in theradial and axial directions.

[0025] Additional features integrated into the body 18 may be covermounts 60 and brace members 62. In this exemplary embodiment, the covermounts 60 threadingly receive the screws 28, thereby securing the cover26 to the body. Extending between the respective cover mounts 60 as wellas between the cover mounts 60 and the integrated bearing structure 48,are bracing members 62 which, in the exemplary embodiment, providetorsional rigidity to the body 18 and the respective integratedfeatures. Additionally, as further discussed below, the bracing members62 may assist in the support and alignment of the cover 26.

[0026] The covers 26 may comprise a number of integrated interiorfeatures that are advantageous to the assembly of the connector 12. Forexample, the cover 26 may comprise integrated buttresses 64. Thebuttresses 64 may be oriented vertically and, when the cover 26 isassembled, may be dimensioned such that the securing member 36 lightlyabuts against the buttresses 64. Additionally, bracing members 62 mayalso be integrally fashioned on the cover 26. The bracing members 62,similar to those on the body 18, may provide alignment assistance andtorsional rigidity to the cover 26.

[0027] Focusing on the actuation member 22 and securing members 36 ofthe present exemplary embodiment, FIG. 2 illustrates that the twomembers may be coupled to one another. In achieving this coupling, theactuation member 22 may comprise a slot 66 through which an engagementpin 68 may be received. The engagement pin 68 may be inserted throughthe slot 66 as well as through a positioning hole 70 located in thelower portion of the securing member 36. Once properly aligned, thesecuring member 36 and the actuation member 22 may be securely coupledby fastening a retaining nut 72 onto the threaded portion of theengagement pin 68. Upon assembly, the disposition of the engagement pin68 within the slot 66 positionably couples the securing member 36 to theactuation member 22. Moreover, as discussed above, the integrated guidechannel 46 of the exemplary embodiment restricts movement of thesecuring member 36 to the axial direction, and, as such, providessupport to the securing member 36. Accordingly, the securing member 36is primarily supported by the actuation member 22 to which it iscoupled.

[0028] In conjunction with a camming surface 74, as defined by theperimeter of the slot 66, the pivotal movement of the actuation member22 directs the axial movement of the securing member 36. In other words,the rotational movement of the actuation member 22 translates into theaxial displacement of the securing member 36. Because the integratedguide channel 46 restricts movement of the securing member to all butthe axial direction, only the axial component of force applied to thesecuring member 36 or engagement pin 68 will result in displacement ofthe securing member 36. Keeping this in mind, the kinetic interactionbetween the camming surface 74 and the engagement pin 68 imparts anumber of forces on the securing member 32, however, only the axialcomponent of the applied force will result in displacement, which, asdiscussed above, is limited to the axial direction. Accordingly, as theactuation member 22 is rotated in a direction generally tangential withrespect to the body 18, the camming surface 74 defines the axialposition of the securing member 32.

[0029] Particulars of the exemplary actuation member 22, slot 66 andcamming surface 74 are more clearly illustrated in regards to FIGS. 3Aand 3B. The actuation member 22 comprises an upper portion 76 coupled toa lower portion 78 by a transition portion 80. In this exemplaryembodiment, the lower portion 78 may be configured to reside furtheroutward, radially, with respect to the body 18 (see FIG. 2).Advantageously, this outward configuration provides additional accessspace between the lower portion 78 and the flexible conduit 14 (seeFIG. 1) to the operator.

[0030] The upper portion 76 of the actuation member 22 comprises boththe pivot opening 54 as well as the slot 66. In this embodiment, theperimeter of the slot 66 defines an arcuate camming surface 74. However,other arrangements are also envisaged. For example, the camming surface74 may be angular in nature. The present arcuate camming surface 74,however, provides a smooth transitional surface. In other words, duringactuation, the interaction between the engagement pin 68 (see FIG. 2)and the camming surface 74 produces a smooth axial displacement of thesecuring member 36 (see FIG. 2). To maintain good mechanical fit, thepivot opening 54 and the slot 66 may be dimensioned to have respectivediameters only slightly larger than the respective pins 50 and 68 theycarry. By dimensioning the opening 54 and slot 66 as such, a moreprecise and controlled movement of the assembly can be achieved.

[0031] Within the slot 66 may be a locking portion 82. In the presentedembodiment, the locking portion 82 receives the engagement pin 68 andreleasably retains the engagement pin 68. By retaining the engagementpin 68, the actuation member 22 may be secured at the defined position.Accordingly, undesired or accidental axial movement of the securingmember 36 may be avoided.

[0032] The exemplary locking portion 82 may comprise an apex 84 thatrestricts movement of the engagement pin 68 within the slot 66. When theengagement pin 68 is brought into abutment with one side of the apex 84,the movement of the pin 68 within the slot 66 is resisted. To overcomethe resistance, an additional pivotal force may be applied to theactuation member 22. The additional force, in turn, may induce a slightelastic deformation (i.e. compression) in the seal 44 (see FIG. 1). Thisslight deformation allows the engagement pin 68 to travel into thelocking portion of the slot. Subsequently, to release the engagement pin68 from the locking portion 84, a pivotal force in the oppositedirection may be applied to the actuation member 22, thereby inducing asimilar compression in the seal 44 for removal of the connector 12 fromthe aircraft. Seal 44 may thus serve as a biasing element in theassembly. Alternatively, other biasing elements may be provided to allowreleasable locking of the actuation member 22 in its engaged position.

[0033] Referring next to FIG. 4, the cross-sectional illustration of theexemplary connector 12 affords a view of the interaction, upon assembly,of the features therein. For example, this figure illustrates thepresently preferred dimensional relationships between the variouscomponents. As one example, the close dimensioning between the bracingmember 62, the actuating member 22 and the integrated bearing structure48 provides supplementary mechanical rigidity to the connector 12.

[0034] Additionally, FIG. 4 illustrates the dependency of the axialposition of the securing member 36 on that of the camming surface 74. Inthe axial direction, the securing member 36 is primarily supported bythe engagement pin 68 which, in turn, is primarily supported, again inthe axial direction, by the camming surface 74. Keeping in mind that theintegrated guide channel 46 as well as certain features on the cover 26restrict movement of the securing member 36 to the axial direction,forces imparted on the engagement pin 68 by the camming surface 74 willcause displacement of the securing member 36 in the axial direction. Inother words, the relative height of the camming surface 74 defines theaxial position of the securing member 36. Accordingly, the rotationalmotion of the actuating member 36, in a direction generally tangentialto the body, translates into axial displacement of the securing member36.

[0035] Referring to FIGS. 5 and 6, operation of the present embodimentis addressed. When the aircraft is docked at the gate, the operator maymanually position the connector 12 into abutment with the aircraft inlet16 (see FIG. 1). At this point, the connector 12 is in the releasedconfiguration as illustrated in FIG. 5. In this configuration, the lowerportions of the actuation members 22 are at offset positions withrespect to one another. Additionally, the securing members 36 are in anupwardly biased position. This upward position, allows a latchingportion (not shown) disposed on the aircraft inlet 16 (see FIG. 1) to befreely inserted into the clamping portion of the securing members 32.

[0036] After the connector 12 is properly positioned with respect to theaircraft inlet 16 and latching portion, the operator may pivotallyactuate the actuation members 22 in a direction generally tangential tothe body and in a direction 86 towards one another, as depicted in FIG.6. Referring also to FIG. 2, the actuation initiates engagement betweenthe camming surface 74 and the engagement pin 68. The camming surface 74directs the clamping portion 38 of the securing member 36 in thedownward direction. This causes the clamping portion 38 to securelyengage with a latching portion (not shown) of the aircraft inlet 16.Moreover, the actuation, of the present embodiment, draws the connector12 into abutting engagement with the inlet 16 and compresses the seal 44(FIG. 1).

[0037] As stated above, the slot 66 (see FIG. 1) may comprise a lockingportion 82 (see FIG. 3A) that secures the position of the respectiveactuating member 22. In this embodiment, the locking portion 82 may beconfigured within the slot 66 such that the locking portion 82 securesthe connector 12 in the fully engaged position thereby maintainingsecured engagement between the aircraft inlet 16 (see FIG. 1) and theconnector 12. In other words, upon final engagement, the locking portionmaintains the actuation members 22 in a parallel configuration, andsimultaneously maintains the securing member 36 in the downwardposition.

[0038] In limiting the movement of the securing member 36 to the axialdirection, a number of advantages may be realized. For example, theaxial movement of the securing member 32 draws the flexible seal 44 intoengagement with the aircraft inlet 16, thereby creating a tight sealbetween the inlet 16 and the connector 12. Additionally, limiting themovement of the securing member 32 to the axial direction reduces thelikelihood of damage to the clamping portion 38. Simply put, thelimitation or axial reduces the potentially damaging affects of slidingor rotational abutment between the clamping portion 38 and the latchingportion of the inlet 16.

[0039] While the invention may be susceptible to various modificationsand alternative forms, specific embodiments have been shown by way ofexample in the drawings and have been described in detail herein.However, it should be understood that the invention is not intended tobe limited to the particular forms disclosed. Rather, the invention isto cover all modifications, equivalents, and alternatives falling withinthe spirit and scope of the invention as defined by the followingappended claims.

1. A preconditioned air connector, comprising: a body having anintegrated bearing structure; a first member pivotably coupled to thebody and including a camming surface that at least partially defines aslot, the first member being at least partially supported by theintegrated bearing structure; an engagement member disposed in the slot;and a second member coupled to the first member via the engagementmember, wherein pivotal actuation of the first member in a directiongenerally tangential to the body directs axial translation of the secondmember from a first position to a second position such that the cammingsurface defines the first and second positions.
 2. The connector asrecited in claim 1, wherein the body comprises an injection moldedplastic.
 3. (canceled).
 4. (canceled).
 5. The connector as recited inclaim 3, wherein the camming surface defines the first and secondpositions.
 6. The connector as recited in claim 1, wherein the secondmember comprises a clamping portion.
 7. The connector as recited inclaim 6, wherein the clamping portion is adapted to releasably securethe connector to an aircraft.
 8. A preconditioned air connector,comprising: a body; and a connection assembly comprising: a first memberhaving a camming surface at least partially defining slot, the firstmember being pivotably coupled to the body such that the first memberactuates in a direction generally tangential to the body; an engagementmember disposed in the slot: and a second member coupled to the firstmember via the engagement member, wherein interaction between theengagement member and the camming surface drives the second member froma first position to a second position, and wherein the engagement memberis disposable at a plurality of locations with respect to the slot. 9.The connector as recited in claim 8, wherein the camming surface isarcuate.
 10. The connector as recited in claim 8, wherein the connectionassembly further comprises a cover securable to the body, wherein thecover comprises a guide portion adapted to guide movement of the secondmember.
 11. The connector as recited in claim 8, wherein the bodycomprises an integrated bearing structure, the bearing structureconfigured to at least partially support the first member.
 12. Theconnector as recited in claim 8, wherein the body comprises an injectionmolded plastic.
 13. The connector as recited in claim 8, wherein theconnector comprises a plurality of connection assemblies.
 14. Theconnector as recited in claim 13, wherein a first connection assembly isdisposed at a first location on the body and a second connectionassembly is disposed at a second location on the body opposite the firstlocation.
 15. The connector as recited in claim 8, wherein the connectoris couplable to an aircraft.
 16. The connector as recited in claim 8,wherein the slot comprises a locking portion adapted to releasablysecure the engagement member with respect to the slot.
 17. Apreconditioned air connector, comprising: a body; a first memberrotatably coupled to the body; and a second member non-rotatably coupledto the body, wherein rotational actuation of the first member in adirection generally tangential to the body actuates the second memberfrom a first axial position with respect to the body to a second axialposition with respect to the body.
 18. (canceled).
 19. The connector asrecited in claim 17, wherein the body comprises an integrated bearingstructure, the bearing structure configured to at least partiallysupport the first member.
 20. A system for routing preconditioned airinto an aircraft, comprising: a conduit adapted to route preconditionedair from a source to the aircraft; and a connector adapted to couple theconduit to the aircraft, the connector comprising: a body; a firstmember rotatably coupled to the body; a second member non-rotatablycoupled to the body, wherein rotational actuation of the first member ina direction generally tangential to the body actuates the second memberin an axial direction with respect to the body.
 21. The system asrecited in claim 20, wherein the first member includes a slot having acamming surface.
 22. The system as recited in claim 21, the cammingsurface being arcuate.
 23. The system as recited in claim 20, whereinthe body comprises an integrated bearing structure adapted to at leastpartially support the first member.
 24. The system as recited in claim20, further comprising a flexible seal disposed between the body and theaircraft.
 25. The system as recited in claim 20, wherein the bodycomprises an injection molded plastic nylon.
 26. A system for routingpreconditioned air into an aircraft, comprising: a flexible conduit fordirecting the preconditioned air from a source to the aircraft; and aconnector configured to couple the conduit to the aircraft, theconnector comprising: a body having an integrated bearing structure; afirst member rotatably coupled to the body and having a slot disposedtherein, the slot comprising an arcuate camming surface; and a secondmember coupled to the first member, the second member having anengagement member coupled thereto, wherein rotational actuation of thefirst member engages the engagement member with the camming surface,thereby actuating the second member from a first axial position withrespect to the body to a second axial position with respect to the body.27. The system as recited in claim 26, wherein the body comprises aninjection molded plastic.
 28. The system as recited in claim 26, whereinthe first member is configured to rotate in a direction generallytangential to the body.
 29. The system as recited in claim 26, whereinthe body comprises an integrated guide portion, wherein the guideportion restricts rotational and radial movement of the second memberwith respect to the body.
 30. The system as recited in claim 26, whereinthe slot comprises a locking portion adapted to releasably secure thesecond member at a desired axial position.
 31. A method for securing apreconditioned air connector, the method comprising: coupling a firstmember to a second member via an engagement member; pivoting the firstmember having an arcuate camming surface in a direction generallytangential to a body, the first member being pivotably coupled to thebody; and driving the second member in an axial direction with respectto the body via the interaction between the engagement member and thecamming surface, such that the camming surface defines the axialposition of the second member.
 32. The method as recited in claim 31,further comprising coupling the connector to a preconditioned airsource.
 33. The method as recited in claim 31, further comprisingrouting the preconditioned air via a conduit.
 34. The method as recitedin claim 32, further comprising coupling the connector to an aircraft.35. The method as recited in claim 31, further comprising supporting thefirst member via an integrated bearing structure of the body.
 36. Apreconditioned air connector, comprising: a tubular body; first andsecond actuation members pivotably coupled to the body and disposedopposite one another, each actuation member having a slot; first andsecond securing members configured to secure the body to an aircraft;and first and second engagement members disposed in the correspondingslots and configured to couple the corresponding actuation members andsecuring member; wherein actuation of the first and second actuationmembers generally tangential to the body and in opposite directions withrespect to one another drives the first and second securing members inan axial direction with respect to the body.
 37. The precondition airconnector as recited in claim 36, wherein the slots each have lockingportions configured to releasably secure the actuation members at adesired position via the engagement members.
 38. The precondition airconnector as recited in claim 36, comprising a guide portion configuredto substantially prevent axial and radial movement of the securingmembers with respect to the body.